Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient Calculator

✖Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.ⓘ Yawing Moment Coefficient [C_n]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%
✖Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing Dynamic Pressure [Q_w]			+10% -10%
✖The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.ⓘ Vertical Tail Moment Arm [𝒍_v]			+10% -10%
✖The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical Tail Area [S_v]			+10% -10%
✖Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical Tail Dynamic Pressure [Q_v]			+10% -10%
✖The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.ⓘ Sideslip Angle [β]			+10% -10%
✖Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.ⓘ Sidewash Angle [σ]			+10% -10%

✖The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient [C_v]

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Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Lift Curve Slope = Yawing Moment Coefficient*Reference Area*Wingspan*Wing Dynamic Pressure/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*(Sideslip Angle+Sidewash Angle))
C_v = C_n*S*b*Q_w/(𝒍_v*S_v*Q_v*(β+σ))
This formula uses 10 Variables

Variables Used

Vertical Tail Lift Curve Slope - (Measured in 1 per Radian) - The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Yawing Moment Coefficient - Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Wing Dynamic Pressure - (Measured in Pascal) - Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.
Vertical Tail Moment Arm - (Measured in Meter) - The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical Tail Area - (Measured in Square Meter) - The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
Vertical Tail Dynamic Pressure - (Measured in Pascal) - Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.
Sideslip Angle - (Measured in Radian) - The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.
Sidewash Angle - (Measured in Radian) - Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.

STEP 1: Convert Input(s) to Base Unit

Yawing Moment Coefficient: 1.4 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 1.15 Meter --> 1.15 Meter No Conversion Required
Wing Dynamic Pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required
Sideslip Angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash Angle: 0.067 Radian --> 0.067 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_v = C_n*S*b*Q_w/(𝒍_v*S_v*Q_v*(β+σ)) --> 1.4*5.08*1.15*0.66/(1.2*5*11*(0.05+0.067))

Evaluating ... ...

C_v = 0.699042735042735

STEP 3: Convert Result to Output's Unit

0.699042735042735 1 per Radian --> No Conversion Required

FINAL ANSWER

0.699042735042735 ≈ 0.699043 1 per Radian <-- Vertical Tail Lift Curve Slope

(Calculation completed in 00.004 seconds)

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< Vertical Tail Contribution Calculators

Vertical Tail Angle of Attack for given Vertical Tail Side Force

LaTeX Go Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Lift Curve Slope

LaTeX Go Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Side Force

LaTeX Go Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure

Vertical Tail Angle of Attack

LaTeX Go Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle

Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient Formula

LaTeX Go

Which flap gives the best lift coefficient?

The double-slotted flap increases the maximum lift coefficient in the same way the single-slotted flap does – by delaying flow separation over the flap element. The key difference is that the double-slotted flap adds a level of boundary-layer control not possible with the single-slotted one.

How to Calculate Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient?

Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient calculator uses Vertical Tail Lift Curve Slope = Yawing Moment Coefficient*Reference Area*Wingspan*Wing Dynamic Pressure/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*(Sideslip Angle+Sidewash Angle)) to calculate the Vertical Tail Lift Curve Slope, Vertical tail lift curve slope for given yawing moment coefficient is a measure of the rate of change of the vertical tail's lift force in response to changes in sideslip angle, normalized by the yawing moment coefficient, and dependent on various aerodynamic and geometric parameters of the aircraft, including the reference area, wingspan, dynamic pressure, and moment arm of the vertical tail. Vertical Tail Lift Curve Slope is denoted by C_v symbol.

How to calculate Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient using this online calculator? To use this online calculator for Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient, enter Yawing Moment Coefficient (C_n), Reference Area (S), Wingspan (b), Wing Dynamic Pressure (Q_w), Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Sideslip Angle (β) & Sidewash Angle (σ) and hit the calculate button. Here is how the Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient calculation can be explained with given input values -> 0.700806 = 1.4*5.08*1.15*0.66/(1.2*5*11*(0.05+0.067)).

FAQ

What is Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient?

Vertical tail lift curve slope for given yawing moment coefficient is a measure of the rate of change of the vertical tail's lift force in response to changes in sideslip angle, normalized by the yawing moment coefficient, and dependent on various aerodynamic and geometric parameters of the aircraft, including the reference area, wingspan, dynamic pressure, and moment arm of the vertical tail and is represented as C_v = C_n*S*b*Q_w/(𝒍_v*S_v*Q_v*(β+σ)) or Vertical Tail Lift Curve Slope = Yawing Moment Coefficient*Reference Area*Wingspan*Wing Dynamic Pressure/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*(Sideslip Angle+Sidewash Angle)). Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft, The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft, The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind & Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.

How to calculate Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient?

How many ways are there to calculate Vertical Tail Lift Curve Slope?

In this formula, Vertical Tail Lift Curve Slope uses Yawing Moment Coefficient, Reference Area, Wingspan, Wing Dynamic Pressure, Vertical Tail Moment Arm, Vertical Tail Area, Vertical Tail Dynamic Pressure, Sideslip Angle & Sidewash Angle. We can use 3 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))
Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area)
Vertical Tail Lift Curve Slope = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Efficiency*(Sideslip Angle+Sidewash Angle))

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